Earth Escape from a Sun-Earth Halo Orbit using Unstable Manifold and Lunar Swingbys
Author:
Affiliation:
1. Department of Aeronautics and Astronautics, Kyushu University
2. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (ISAS/JAXA)
Publisher
Japan Society for Aeronautical and Space Sciences
Subject
Space and Planetary Science,Aerospace Engineering
Link
https://www.jstage.jst.go.jp/article/tjsass/59/5/59_T-15-7/_pdf
Reference17 articles.
1. 1) Villac, B. F. and Scheeres, D. J.: Escaping Trajectories in the Hill Three-Body Problem and Applications, J. Guid. Control Dynam., 26 (2003), pp. 224–232.
2. 2) Nakamiya, M., Yamakawa, H., Scheeres, D. J., and Yoshikawa, M.: Interplanetary Transfers between Halo Orbits: Connectivity between Escape and Capture Trajectories, J. Guid. Control Dynam., 33 (2010), pp. 803–813.
3. 3) Mingotti, G., Topputo, F., and Bernelli-Zazzera, F.: Earth–Mars Transfers with Ballistic Escape and Low-Thrust Capture, Celest. Mech. Dynam. Astron., 110 (2011), pp. 169–188.
4. 4) Farquhar, R.: The Flight of ISEE-3/ICE: Origins, Mission History, and a Legacy, J. Astronaut. Sci., 49 (2001), pp. 23–73.
5. 5) Kawaguchi, J., Yamakawa, H., Uesugi, T., and Matsuo, H.: On Making Use of Lunar and Solar Gravity Assists in LUNAR-A, PLANET-B Missions, Acta Astronaut., 35 (1995), pp. 633–642.
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